Strength of stiffened 2024-T3 aluminum panels with multiple site damage

Smith B., HIJAZİ A. L. A., Haque A., Myose R.

Journal of Aircraft, cilt.38, sa.4, ss.764-768, 2001 (SCI-Expanded, Scopus) identifier

  • Yayın Türü: Makale / Tam Makale
  • Cilt numarası: 38 Sayı: 4
  • Basım Tarihi: 2001
  • Doi Numarası: 10.2514/2.2829
  • Dergi Adı: Journal of Aircraft
  • Derginin Tarandığı İndeksler: Science Citation Index Expanded (SCI-EXPANDED), Scopus
  • Sayfa Sayıları: ss.764-768
  • İstanbul Gelişim Üniversitesi Adresli: Evet

Özet

Two modified linkup models were developed for determining the critical stress based on linkup (ligament failure) of 2024-T3 aluminum panels with multiple site damage. These models were developed for use with standard Military Handbook for Metallic Materials and Elements for Aerospace Vehicle Structures (MIL-HDBK-5G) yield strength values. For this investigation, ligament failure stresses predicted by these models are compared with test stresses determined from a variety of stiffened panels including single-bay panels with the lead crack centered between stiffeners and two-bay panels with the lead crack centered beneath a severed stiffener. The stresses predicted by the modified linkup models correlate well with the test data. The results of this investigation should add to the understanding of the extent to which nonlinear behavior can be modeled with simplified engineering models.